AircraftDirectives
MembershipSign inCreate free account
Menu
Airworthiness Directive

AD 99-09-20 64 FR 23016 Active

Federal Aviation Administration · 14 CFR part 39

Requires initial and repetitive visual inspections and verification of the torque of the bolts on the main rotor hub.

Federal Register (opens in a new tab)FAA DRS (opens in a new tab)

FR document
99-10669
Amendment
39-11153
Published
1999-04-29
Effective
1999-05-14
Models covered
1

Last live check: 2026-08-19

Printed from https://aircraftdirectives.com/ad/99-09-20 · AircraftDirectives restates official FAA and manufacturer records; the official sources named on this sheet control. Not an airworthiness determination.

This page is a reference Record, not an airworthiness or compliance determination. Official FAA and manufacturer sources control over our restatement, subject to governing law. Check applicability, current requirements and incorporated documents before acting. The owner or operator remains responsible for airworthiness and required records under 14 CFR 91.403 and 91.417, as applicable. Terms of Use: /terms.

Opens your browser's print dialog. Choose “Save as PDF” to export a file. Keyboard: Ctrl+P or Cmd+P.

AD

99-09-20

FR doc 99-10669 · 64 FR 23016

AD 99-09-20Published 1999-04-29Effective 1999-05-14

FAA rule - 14 CFR 39

FAA rule. Compliance with an applicable AD is required under 14 CFR 39.7. Check its effective date, applicability, compliance times and current status.

Requires initial and repetitive visual inspections and verification of the torque of the bolts on the main rotor hub.

Full official abstract

This amendment adopts a new airworthiness directive (AD) that is applicable to BHTC Model 222, 222B, and 222U helicopters. This action requires initial and repetitive visual inspections and verification of the torque of the bolts on the main rotor hub. This amendment is prompted by a report of fatigue cracks around the bolt holes of the main rotor pitch horn (pitch horn) and a cracked main rotor flapping bearing assembly (flapping bearing assembly) on a BHTC Model 222 helicopter. This condition, if not corrected, could result in fretting-induced fatigue cracking of the flapping bearing assembly and around the bolt holes of the pitch horn, loss of the rotor system, and subsequent loss of control of the helicopter.

More directives for Bell 222

  1. AD 2026-17-51 Airworthiness Directives; Bell Textron Canada Limited Helicopters Effective 2026-09-14
  2. AD 2021-19-01 Airworthiness Directives; Bell Textron Canada Limited Helicopters Effective 2021-10-13
  3. AD 2016-08-17 Airworthiness Directives; Bell Helicopter Textron Canada Helicopters Effective 2016-05-31
  4. AD 2013-18-06 Airworthiness Directives; Bell Helicopter Textron Canada Limited (Bell) ... Effective 2013-10-17
  5. AD 2010-26-51 Airworthiness Directives; Bell Helicopter Textron Canada Limited (BHTC) ... Effective 2011-03-25

All Bell 222 directives

View on Federal Register (opens in a new tab) View this AD in FAA DRS (opens in a new tab) Print AD packet (opens the full Federal Register document in a new tab)

Applies to 1 model in our index